U.S. patent application number 15/663462 was filed with the patent office on 2019-01-31 for endwall cooling system.
The applicant listed for this patent is Rolls-Royce Corporation. Invention is credited to Tony A. Lambert, John A. Weaver.
Application Number | 20190032495 15/663462 |
Document ID | / |
Family ID | 65037900 |
Filed Date | 2019-01-31 |
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United States Patent
Application |
20190032495 |
Kind Code |
A1 |
Weaver; John A. ; et
al. |
January 31, 2019 |
ENDWALL COOLING SYSTEM
Abstract
An air distribution system for cooling a component in a heated
gas environment may be provided, where the air distribution system
includes a wall and a plate. The wall includes an inner surface, an
outer surface configured to be exposed to the heated gas
environment, and a protrusion extending from the inner surface of
the wall. The plate is fixedly coupled to the protrusion and is
space apart from the inner surface of the wall. The plate includes
an outer edge. A passage is defined between the plate and the inner
surface of the wall. The inlet of the passage is defined by the
outer edge of the plate.
Inventors: |
Weaver; John A.;
(Indianapolis, IN) ; Lambert; Tony A.;
(Brownsburg, IN) |
|
Applicant: |
Name |
City |
State |
Country |
Type |
Rolls-Royce Corporation |
Indianapolis |
IN |
US |
|
|
Family ID: |
65037900 |
Appl. No.: |
15/663462 |
Filed: |
July 28, 2017 |
Current U.S.
Class: |
1/1 |
Current CPC
Class: |
F05D 2250/12 20130101;
F01D 25/12 20130101; F05D 2250/141 20130101; F01D 5/145 20130101;
F05D 2260/20 20130101; F04D 29/5846 20130101; F01D 5/187 20130101;
F04D 29/2272 20130101; F04D 29/2255 20130101; F05D 2240/81
20130101; F05D 2260/22141 20130101; F01D 9/041 20130101; F01D 5/188
20130101; Y02T 50/60 20130101 |
International
Class: |
F01D 5/18 20060101
F01D005/18; F04D 29/22 20060101 F04D029/22; F01D 25/12 20060101
F01D025/12; F01D 5/14 20060101 F01D005/14; F04D 29/58 20060101
F04D029/58 |
Claims
1. An air distribution system for cooling a component in a heated
gas environment of a gas turbine engine, comprising: a wall
comprising an inner surface, an outer surface configured to be
exposed to the heated gas environment, and a protrusion extending
from the inner surface of the wall; and a plate spaced apart from
the inner surface of the wall, the plate comprising an outer edge,
the plate fixedly coupled to the protrusion, wherein a passage is
defined between the plate and the inner surface of the wall, and
wherein an inlet of the passage is defined by the outer edge of the
plate.
2. The air distribution system of claim 1, wherein the wall
comprises an opening extending between the inner surface and the
outer surface of the wall, the opening defining an outlet of the
passage.
3. The air distribution system of claim 2, wherein the opening of
the wall is arranged proximate to the protrusion.
4. The air distribution system of claim 2, wherein the opening is
positioned on the wall so as to maximize distance between the outer
edge of the plate and the opening of the wall.
5. The air distribution system of claim 1, wherein the protrusion
is fixedly coupled to a center of the plate.
6. The air distribution system of claim 1, wherein the protrusion
is fixedly coupled to a portion of the outer edge of the plate.
7. The air distribution system of claim 1, wherein one of the wall
or the plate comprises a rib extending into the passage, wherein
the rib is configured to direct air flow from the inlet of the
passage to an outlet of the passage.
8. The air distribution system of claim 1, wherein the plate
comprises an intact surface extending from a first outer edge of
the plate to an opposing second outer edge of the plate.
9. The air distribution system of claim 1, wherein one of the wall
or the plate comprises a plurality of pins extending in the
passage, and wherein the plurality of pins are shaped and arranged
to create turbulence in a fluid that passes through the
passage.
10. The air distribution system of claim 1, comprising a plurality
of plates and a plurality of protrusions, wherein each plate is
coupled one of the plurality of protrusions, wherein each of the
plurality of plates is spaced apart from each another, and wherein
the inlet of the passage is at least partially defined by a gap
between the respective outer edges of at least two of the plurality
of plates.
11. A turbine vane comprising: a wall comprising an inner surface,
an outer surface, and a protrusion extending from the inner surface
of the wall; a plate spaced apart from the inner surface of the
wall, the plate comprising an outer edge, wherein the plate is
fixedly coupled to the protrusion; and an airfoil extending
outwardly from the outer surface of the wall, wherein a passage is
defined between the plate and the inner surface of the wall, and
wherein an inlet of the passage is defined by the outer edge of the
plate.
12. The turbine vane of claim 11, wherein a perimeter of the plate
defined by the outer edge of the plate is greater than a perimeter
of the protrusion which is fixedly coupled to the plate.
13. The turbine vane of claim 11, further comprising a cavity
within the airfoil, the passage having an outlet which is in fluid
communication with the cavity of the airfoil.
14. The turbine vane of claim 13, wherein the airfoil comprises a
boss which extends inwardly from the inner surface of the wall,
wherein the outlet of the passage is defined by an opening in the
boss.
15. The turbine vane of claim 14, wherein the protrusion is the
boss of the airfoil.
16. The turbine vane of claim 15, wherein the plate encircles the
boss of the airfoil.
17. The turbine vane of claim 16, wherein the wall comprises a
raised element extending transversely to and aligned with the outer
edge of the plate, wherein the inlet of the passage is at least
partially defined by a gap between the raised element of the wall
and the outer edge of the plate.
18. A method of cooling a component of a turbine vane comprising:
supplying cooling air to a passage, wherein the passage is defined
by a wall of the turbine vane and a plate spaced apart from the
wall, wherein the plate is fixedly coupled to a protrusion which
extends between the plate and the wall, and wherein an inlet of the
passage is defined by an outer edge of the plate; and releasing the
cooling air from the passage through an outlet of the passage.
19. The method of claim 18, wherein the cooling air is released
through an opening in the wall to an outer surface of the wall.
20. The method of claim 18, wherein the cooling air is released
into a cavity of an airfoil of the turbine vane.
Description
TECHNICAL FIELD
[0001] This disclosure relates to cooling systems, and, in
particular to cooling systems for gas turbine engines.
BACKGROUND
[0002] Components placed within a turbine flow path of a gas
turbine engine undergo considerable thermal stress from combusted
gases passing through the turbine flow path. An endwall of the
turbine flow path may be cooled by air delivered to the outside of
the turbine flow path to prevent deformation, fracturing, or
cracking of the endwall.
BRIEF DESCRIPTION OF THE DRAWINGS
[0003] The embodiments may be better understood with reference to
the following drawings and description. The components in the
figures are not necessarily to scale. Moreover, in the figures,
like-referenced numerals designate corresponding parts throughout
the different views.
[0004] FIG. 1 illustrates a top-down cross-sectional view of a
first example of an endwall cooling system;
[0005] FIG. 2 illustrates a side cross-sectional view of the first
example of the endwall cooling system shown in FIG. 1;
[0006] FIG. 3 illustrates a top-down partial cross-sectional view
of a second example of an endwall cooling system;
[0007] FIG. 4 illustrates a partial side cross-sectional view of
the second example of the endwall cooling system shown in FIG.
3;
[0008] FIG. 5 illustrates a top-down partial cross-sectional view
of a third example of an endwall cooling system;
[0009] FIG. 6 illustrates a side cross-sectional view of the third
example of the endwall cooling system shown in FIG. 5;
[0010] FIG. 7 illustrates a flow diagram of an example of a method
of cooling a component of a turbine vane;
[0011] FIG. 8 illustrates a cross-sectional view of an example of a
gas turbine engine; and
[0012] FIG. 9 illustrates a cross-sectional view of a portion of an
example of a turbine section of a gas turbine engine.
DETAILED DESCRIPTION
[0013] In some examples, an impingement plate may be brazed to the
outer edge of an endwall of a turbine flow path of a gas turbine
engine to create a cooling passageway between the impingement plate
and the endwall. The impingement plate may have numerous small
openings which control the flow of air, breaking up laminar flow of
the air within the cooling passage and aiding heat transfer from
the endwall to the air. However, differences in thermal expansion
between the endwall and the impingement plate may cause the braze
between the impingement plate and the endwall to fail. Such a
failure may result in inadequate cooling of the endwall and damage
to the turbine section.
[0014] An air distribution system, for example, is provided for
cooling a component in a heated gas environment, such as a turbine
chamber of a gas turbine engine. The air distribution system
includes a wall and a plate. The wall includes having an inner
surface, an outer surface, and a protrusion extending from the
inner surface of the wall. The outer surface of the wall is
configured to be exposed to the heated gas environment. The plate
is spaced apart from the inner surface of the wall and is fixedly
coupled to the protrusion. The plate includes an outer edge. A
passage is defined between the plate and the inner surface of the
wall. An inlet of the passage is defined by the outer edge of the
plate.
[0015] One interesting feature of the systems and methods described
below may be that the air distribution system may provide cooling
to the wall exposed to the heated gas environment more efficiently
than some other systems. Alternatively, or in addition, an
interesting feature of the systems and methods described below may
be that the air distribution system decreases the possibility of
cracking or fracturing due to differences in thermal expansion.
[0016] FIGS. 1 and 2 illustrate cross-sectional views of a first
example of an air distribution system 11 including a wall 10 and a
plate 12. The wall 10 may be any object which is shaped and
configured to form a portion of the inner surface of a turbine flow
path. Examples of the wall 10 may include an end wall of a gas
turbine engine, a flat panel, a curved panel, or a casing having a
complex shape and being adapted to be interlocked with other
casings. The wall 10 may be made of any material capable of
withstanding the heated gas environment of the turbine flow path,
such as steel, titanium, or a ceramic matrix composite (CMC).
[0017] The wall 10 may include an inner surface 30 and an outer
surface 32. The outer surface 32 may be any surface of the wall 10
that is directly exposed to the heated gas environment of the
turbine flow path (see the turbine flow path 76 in FIG. 9). The
outer surface 32 may be made of the same material as the wall 10,
or may include an additional coating to provide better thermal
resistance. The inner surface 30 may be any surface opposite of the
outer surface 32 and that is not directly exposed to the heated gas
environment of the turbine flow path 76. The inner surface 30 may
be made of the same material as the wall 10 or may comprise an
additional coating to provide oxidation protection or increase
frictional force on air traveling over the inner surface 30. The
inner surface 30 may also include a texturing which increases the
frictional force on air traveling over the inner surface 30 to
prevent or limit laminar flow over the inner surface 30 and
increase cooling efficiency.
[0018] The wall 10 may include multiple outlets 24 extending
between the inner surface 30 and the outer surface 32 of the wall
10. The outlets 24 may be any feature which allows fluid
communication between the inner surface 30 and the outer surface 32
of the wall 10. Examples of the outlets 24 may include holes,
vents, or apertures. The outlets 24 may be clustered around a
particular area of the wall 10, spread evenly across the wall 10,
or arranged in any other manner. The size of the outlets 24 may be
consistent among the outlets 24 or may vary with respect to the
position of each of the outlets 24 on the wall 10.
[0019] The wall 10 may include a raised surface 20 which extends
inwardly from the inner surface 30. The raised surface 20 may be
any portion of the wall 10 that defines a boundary for the area of
the wall 10 to be cooled. Examples of the raised surface 20 may
include a barrier, a boss, or a panel. The raised surface 20 may be
located further from the outer surface 32 of the wall 10 than the
inner surface 30 of the wall 10 and therefore may experience less
thermal stress than other portions of the wall 10. Heat may be
conducted from the outer surface 32 of the wall 10 such that the
raised surface 20 experiences more thermal stress than other
components of the air distribution system 11. The raised surface 20
may be made of the same materials as the wall 10 or may be made of
a less heat resistant material than the wall 10. The raised surface
20 may be configured to be coupled to other portions of a gas
turbine engine (60 in FIG. 8) by bolting, welding, or brazing. In
some embodiments, the raised surface 20 may define a complete
boundary of another portion of the wall 10. In such embodiments,
the portion of the wall 10 within the boundary of the raised
surface 20 may be the portion of the wall 10 to be cooled.
[0020] The plate 12 is spaced apart from the inner surface 30 of
the wall 10. The plate 12 may be an object that at least partially
covers the inner surface 30 of the wall 10 and which directs the
flow of air proceeding toward the wall 10. Examples of the plate 12
may include a flat slab, a hemispheric disc, and a thin slice of
rigid material. The plate 12 may be made of any material
sufficiently rigid to direct airflow and capable of withstanding
thermal stress conducted to the plate 12 from the wall 10. Examples
of materials for the plate 12 may include steel, titanium, and CMC.
The plate 12 may experience less thermal stress than the wall 10;
therefore, in some embodiments, a coefficient of thermal expansion
of the plate 12 may be less than or equal to a coefficient of
thermal expansion of the wall 10.
[0021] The plate 12 includes an outer edge 18 which defines the
boundary of the plate 12 covering the wall 10. The outer edge 18
may have a circular, rectangular, or other more complex shape. In
some examples, the shape of the outer edge 18 may be dependent upon
the number of plates 12 in the air distribution system 11 and the
shape of the wall 10 and the raised surface 20. The raised surface
20 of the wall 10 may extend transversely to, and may be aligned
with, the outer edge 18 of the plate 12, defining a gap between the
raised surface 20 and the outer edge 18. A portion of the outer
edge 18 of the plate 12 may also extend transversely to and may be
aligned with the outer edge 18 of a different plate 12, defining a
gap between the outer edge 18 of the plate 12 and the outer edge 18
of a different plate 12.
[0022] The plate 12 may have an intact surface extending from a
first outer edge 18 of the plate to an opposing second outer edge
18 of the plate, the intact surface having no openings or holes.
The intact surface may prevent air from passing through the plate
12 and force air to the outer edge 18 of the plate 12.
[0023] The air distribution system 11 may also include a protrusion
16 extending from the inner surface 30 of the wall 10 to the plate
12. The protrusion 16 may be any feature which is coupled to and
spaces apart the wall 10 and the plate 12. Examples of the
protrusion 16 may include a strut, a column, or a raised element.
The protrusion 16 may be made of the same material as either the
plate 12 or the wall 10 including steel, titanium, or CMC. The
protrusion 16 may be formed integrally with the wall 10 or with the
plate 12.
[0024] As shown in FIG. 1, the protrusion 16 may include a surface
46 which may be fixedly coupled to the plate 12. Alternatively, in
some embodiments, the protrusion 16 may be fixedly coupled to the
wall 10. The surface 46 may be fixedly coupled to the plate 12 by a
variety of methods, such as bonding, brazing, or welding. The
protrusion 16 may experience thermal stress conducted from the wall
10. Therefore, the size of the surface 46 of the protrusion 16 may
be limited in order to reduce the risk of cracking or breaking the
connection of the protrusion 16 with either of the wall 10 or the
plate 12 due to differences in thermal expansion. For example, the
surface 46 may be circular in shape to limit the surface area of
the surface 46 to reduce the differences in thermal expansion while
keeping the surface area large enough to couple to the plate 12. In
some examples, the surface 46 of the protrusion 16 may have a
surface area between 0.005 in.sup.2 and 0.2 in.sup.2. The surface
area of the surface 46 of the protrusion 16 may be less than a
surface area of the plate 12: for example, between 2% and 10% of
the surface area of the plate 12. Similarly, the surface 46 of the
protrusion may have a perimeter 34 which is less than a perimeter
of the outer edge 18 of the plate 12: for example, between 2% and
35% of the perimeter of the outer edge 18 of the plate 12.
[0025] In some embodiments, the protrusion 16 may be fixedly
coupled to the plate 12 at the center of the plate 12. The center
of the plate 12 may be a point within the outer edge 18 of the
plate 12 that maximizes the average distance of the outer edge 18
to that point. In other embodiments, the protrusion 16 may be
fixedly coupled to the plate at a point offset from the center of
the plate 12. In other embodiments, the protrusion 16 may be
positioned wherever the thermal stress on the protrusion 16 may be
minimized or limited.
[0026] A passage 44 is defined between the plate 12 and the inner
surface 30 of the wall 10. The passage 44 may be any space which is
open to fluid flow. Examples of the passage 44 may include a
channel, a tube, or a conduit. Air may enter into the passage 44
through an inlet 22 and exit from the passage 44 through an outlet
24. The inlet 22 may be any space which allows air to enter the
passage 44. Examples of the inlet 22 may include an opening, a gap,
or a duct. As shown in FIGS. 1 and 2, the inlet 22 is defined by a
gap between the outer edge 18 of the plate 12 and raised surface 20
of the wall 10.
[0027] The outlet 24 may be any space which allows air to exit the
passage 44. Examples of the outlet 24 may include an opening, a
gap, or a duct. In some embodiments, for example, as shown in FIG.
1, the outlet 24 of the passage 44 may defined by an opening
extending through the wall 10 from the inner surface 30 to the
outer surface 32. Air passing through the passage 44 may be
delivered at a higher pressure than the pressure of the hot gas
environment. Therefore, air may flow into the hot gas environment
from the passage 44 to cool the outer surface 32 of the wall
10.
[0028] The outlet 24 may be positioned wherever thermal stress on
the wall 10 is the highest. Alternatively, the outlet 24 may be
positioned proximate to the protrusion 16 to provide additional
direct cooling to the protrusion 16 and avoid differential thermal
expansion between the protrusion 16 and either of the plate 12 or
the wall 10. The outlet 24 may be proximate when the outlet 24 is
between 0.01 inches and 1.0 inches from the protrusion 16. The
average distance for air to travel between the inlet 22 and the
outlet 24 may be evenly distributed to ensure even cooling of the
wall 10 as the air passes over the inner surface 30. For example,
as shown in FIG. 1, the protrusion 16 may be arranged at the center
of the plate 12, and a plurality of outlets 24 may encircle the
protrusion 16 to allow relatively even paths for air to travel from
the inlet 22 at the outer edge 18 of the plate 12 to one of the
plurality of outlets 24.
[0029] The passage 44 may include a rib 26 extending along a length
of the passage 44 to compartmentalize the air and better direct the
air from the inlet 22 to the outlet 24. The rib 26 may be any
structure configured to direct the flow of air through the passage
44. Examples of the rib 26 may include a strut, a wall, or a ridge.
The rib 26 may be fixedly coupled or formed as a part of one of the
plate 12 or the wall 10. In some embodiments, the rib 26 may only
be coupled to the wall 10, while the plate 12 rests on top of the
rib 26 and having free range of movement across the rib 26. Such a
configuration may allow free movement between the plate 12 and the
rib 26 that may result from thermal expansion. The rib 26 may be
made from any material sufficient to withstand the thermal stress
within the passage 44, such as steel, titanium, or CMC. As shown in
FIG. 1, a plurality of ribs 26 may be arranged in a pattern to
compartmentalize and direct the flow of air through the passage 44.
The ribs 26 may be arranged in symmetric patterns or have similar
volumes of space between the ribs 26 to ensure even air flow
throughout the passage 44.
[0030] The passage 44 may also include a pin 28 extending inwardly
from the inner surface 30 of the wall 10. The pin 28 may be any
object which, when placed in the passage 44, increases the
turbulence of air passing through the passage 44. Examples of the
pin 28 may include a cylinder, a cone, or a complex shape (e.g., a
turbulator rib) meant to break up laminar airflow. Increasing the
turbulent flow of the air through the passage 44 may increase the
efficiency of heat transfer within the passage 44 by reducing or
eliminating a boundary layer from forming along the inner surface
30 of the wall 10. The pin 28 may be made from any material
sufficient to withstand the thermal stress within the passage 44,
such as steel, titanium, or CMC. The pin 28 may extend outward from
the inner surface 30 such that the plate 12 rests upon the pin 28
while maintaining free range of motion across the pin 28. In other
embodiments, such as shown in FIG. 2, the pin 28 may extend outward
from the inner surface 30 such that a gap 36 is formed between the
pin 28 and the plate 12. As shown in FIG. 1, a plurality of pins 28
may be place throughout the inner surface 30 to create turbulence
and break up laminar flow of air passing through the passage 44.
The pins 28 may have a diameter between 0.02 inches to 0.15
inches.
[0031] FIGS. 3 and 4 illustrate cross-sectional views of a second
example of an air distribution system 11 including the wall 10, the
plate 12, and an airfoil 14. As air is delivered to the wall 10,
air may also be delivered to the airfoil 14 through a cavity 40
extending through the airfoil 14. The airfoil 14 may be any body
extending outwardly into the heated gas environment from the outer
surface 32 of the wall 10. Examples of the airfoil 14 may include
turbine vanes, struts, or turbine blades. The airfoil 14 may
include a bus 38 which encircles the cavity 40 and extends inwardly
from the inner surface 30 of the wall 10. The cavity 40 may be any
space within the airfoil 14 configured to receive and distribute
air to the airfoil 14 for cooling purposes. Examples of the cavity
40 may include a corridor, an enclosure, or a chamber. The bus 38
may be any component of the airfoil 14 which extends inwardly from
the inner surface 30 of the wall 10 and which restricts the flow of
air from the passage 44. Examples of the bus 38 may include a
partition, a ridge, or a barrier.
[0032] As shown in FIGS. 3 and 4, the protrusion 16 may be located
on the side of the wall 10 or may be a portion of the wall 10. A
portion of the outer edge 18 of the plate 12 may be fixedly coupled
to surface 46 of the protrusion 16. Where the protrusion 16 is
located on the side of the wall 10, the protrusion 16 may be
aligned with the raised surface 20 of the wall 10. The surface 46
of the protrusion 16 may be vertically aligned with the raised
surface 20 or may be vertically offset from the raised surface 20
such, once the plate 12 is fixedly coupled to the protrusion 16,
the outer edge 18 of the plate 12 is above, below, or vertically
aligned with the raised surface 20.
[0033] As shown in FIGS. 3 and 4, the outlets 24 of the passage 44
may be located along the side of the wall 10, as close as possible
to the protrusion 16, to allow adequate cooling of the protrusion
16. In some embodiments, the outlets 24 may be located in the
protrusion 16 to allow air purge gaps between walls 10 and cool
adjacent components. In some embodiments, the inlet 22 of the
passage 44 may be located between two adjacent plates 12, a gap
between the respective outer edges 18 of each plate 12 defining the
inlet 22. To accommodate complex shapes within the wall 10 created
by the airfoil 14, multiple plates 12 may be used to cover the wall
10 and direct air to the passage 44 beneath the plates 12. Gaps
between the raised surface 20 of the wall 10 and the plates 12 may
define the inlets 22 of the passage 44. The cavity 40 may remain
uncovered by the plates 12 to provide direct access for the air to
flow into the airfoil 14.
[0034] In some embodiments, ribs 26 may be arranged across plates
12 to partition and direct the flow of air from the inlets 22
toward the outlets 24. As shown in FIG. 3, the ribs 26 may be
arranged between adjacent airfoils 14 in parallel rows, extending
from the outlets 24 located at a first side of the wall 10 to
outlets 24 located at a second side of the wall 10. A plurality of
pins 28 may be arranged between the ribs 26 to decrease laminar
flow of air within the passage 44 and increase the efficiency of
heat transfer from the wall 10.
[0035] FIGS. 5 and 6 illustrate cross-sectional views of a third
example of an air distribution system 11 including the wall 10, the
plate 12, and the airfoil 14. As shown in FIGS. 5 and 6, the
protrusion 16 may be a portion of the bus 38 of the airfoil 14. In
such an embodiment the plate 12 may be fixedly coupled to a portion
or the entirety of the circumference of the bus 38. In such
embodiments, the plate 12 may radiate outwardly from the bus 38 to
cover the wall 10 and define the passage 44. The interior of the
plate 12 may be open to allow air to freely enter the cavity 40 of
the airfoil 14. Where multiple airfoils 14 are present, multiple
plates 12 may be placed alongside one another, each radiating
outwardly from their respective airfoil 14. The inlet 22 of the
passage 44 may be defined by gaps formed between adjacent plates 12
and between the plates 12 and the raised surface 20 of the wall 10.
The outlet 24 of the passage 44 may be located within the bus 38,
directing air exiting the passage 44 into the cavity 40 of the
airfoil 14.
[0036] FIG. 7 illustrates a flow diagram of an example of a system
to cooling a component of a turbine vane (70 in FIG. 9) (100). The
steps may include additional, different, or fewer operations than
illustrated in FIG. 7. The steps may be executed in a different
order than illustrated in FIG. 7.
[0037] The wall 10 may be cooled (100) by initially supplying
cooling air to the passage 44 (102). The passage 44 may be defined
between the wall 10 and the plate 12, where the plate 12 is spaced
apart from the wall 10. A protrusion 16 extends between the plate
12 and the wall 10, where the protrusion 16 is fixedly coupled to
the plate 12. The cooling air is supplied to the passage 44 at an
inlet 22 defined by the outer edge 18 of the plate 12.
[0038] Once the cooling air has been supplied to the passage 44
(102), the cooling air may be released from the passage 44 (104)
through the outlet 24 of the passage 44. The outlet 24 may be
located at the opening in the wall 10 to the outer surface 32 of
the wall 10. Alternatively, the air may be released into a cavity
40 of the airfoil 14.
[0039] Each component may include additional, different, or fewer
components. For example, the passage 44 may comprise a plurality of
inlets 22 and outlets 24. Additionally, the wall 10 and the plate
12 may comprises a plurality of ribs 26 and pins 28 extending into
the passage 44.
[0040] The system (100) may be implemented with additional,
different, or fewer components. For example, a plurality of plates
12 may be used to define the passage 44. Additionally, the
protrusion 16 may be formed from a portion of the wall 10 or from
the bus 38 of the airfoil 14 extending inwardly from the inner
surface 30 of the wall 10.
[0041] The logic illustrated in the flow diagrams may include
additional, different, or fewer operations than illustrated. The
operations illustrated may be performed in an order different than
illustrated.
[0042] FIG. 8 is a cross-sectional view of a gas turbine engine 60
for propulsion of, for example, an aircraft. Alternatively or in
addition, the gas turbine engine 60 may be used to drive a
propeller in aquatic applications, or to drive a generator in
energy applications. The gas turbine engine 60 may include an
intake section 80, a compressor section 62, a combustion section
64, a turbine section 66, and an exhaust section 82. During
operation of the gas turbine engine 60, fluid received from the
intake section 80, such as air, travels along the direction D1 and
may be compressed within the compressor section 62. The compressed
fluid may then be mixed with fuel and the mixture may be burned in
the combustion section 64. The combustion section 64 may include
any suitable fuel injection and combustion mechanisms. The hot,
high pressure fluid may then pass through the turbine section 66 to
extract energy from the fluid and cause a turbine shaft 68 of a
turbine 84 in the turbine section 66 to rotate, which in turn
drives the compressor section 62. Discharge fluid may exit the
exhaust section 82.
[0043] As noted above, the hot, high pressure fluid passes through
the turbine section 66 during operation of the gas turbine engine
60. As the fluid flows through the turbine section 66, the fluid
passes between alternating blades 72 and vanes 70 causing the
turbine 84 to rotate. The rotating turbine 84 may turn a shaft 68
in a rotational direction D2, for example. The blades 72 may rotate
around an axis of rotation, which may correspond to a centerline X
of the turbine 84 in some examples. The vanes 70 may remain
stationary relative to the blades 72 while the turbine 84 is
rotating.
[0044] FIG. 9 is a cross-sectional view of a portion of an example
of the turbine section 76. The turbine vane 70 may extend across
the turbine flow path 76 and may be coupled to an outer combustion
liner 74 and an inner combustion liner 78. Air for cooling may be
delivered to the passage 44 from a hub 86 adjacent to either of the
inner combustion liner 78 or the outer combustion liner 74. The air
flows along the direction D3 from the hub 86, through the passage
44, and into the turbine flow path 76 to cool the wall 10. As shown
in FIG. 9, the wall 10 may be a portion of the turbine vane 70
which extends along the surface of the turbine flow path 76 and
allows the turbine vane 70 to complete the turbine flow path
between the upstream and downstream components.
[0045] To clarify the use of and to hereby provide notice to the
public, the phrases "at least one of <A>, <B>, . . .
and <N>" or "at least one of <A>, <B>, . . .
<N>, or combinations thereof" or "<A>, <B>, . . .
and/or <N>" are defined by the Applicant in the broadest
sense, superseding any other implied definitions hereinbefore or
hereinafter unless expressly asserted by the Applicant to the
contrary, to mean one or more elements selected from the group
comprising A, B, . . . and N. In other words, the phrases mean any
combination of one or more of the elements A, B, . . . or N
including any one element alone or the one element in combination
with one or more of the other elements which may also include, in
combination, additional elements not listed.
[0046] While various embodiments have been described, it will be
apparent to those of ordinary skill in the art that many more
embodiments and implementations are possible. Accordingly, the
embodiments described herein are examples, not the only possible
embodiments and implementations.
[0047] The subject-matter of the disclosure may also relate, among
others, to the following aspects:
1. An air distribution system for cooling a component in a heated
gas environment, comprising:
[0048] a wall comprising an inner surface, an outer surface
configured to be exposed to the heated gas environment, and a
protrusion extending from the inner surface of the wall; and
[0049] a plate spaced apart from the inner surface of the wall, the
plate comprising an outer edge, the plate fixedly coupled to the
protrusion, wherein a passage is defined between the plate and the
inner surface of the wall, and wherein an inlet of the passage is
defined by the outer edge of the plate.
2. The air distribution system of aspect 1, wherein the wall
comprises an opening extending between the inner surface and the
outer surface of the wall, the opening defining an outlet of the
passage. 3. The air distribution system of aspect 2, wherein the
opening of the wall is arranged proximate to the protrusion. 4. The
air distribution system of any of aspects 2 and 3, wherein the
opening is positioned on the wall so as to maximize distance
between the outer edge of the plate and the opening of the wall. 5.
The air distribution system of any of aspects 1-4, wherein the
protrusion is fixedly coupled to a center of the plate. 6. The air
distribution system of any of aspects 1-4, wherein the protrusion
is fixedly coupled to a portion of the outer edge of the plate. 7.
The air distribution system of any of aspects 1-6, wherein one of
the wall or the plate comprises a rib extending into the passage,
wherein the rib is configured to direct air flow from the inlet of
the passage to an outlet of the passage. 8. The air distribution
system of any of aspects 1-7, wherein the plate comprises an intact
surface extending from a first outer edge of the plate to an
opposing second outer edge of the plate. 9. The air distribution
system of any of aspects 1-8, wherein one of the wall or the plate
comprises a plurality of pins extending in the passage, and wherein
the plurality of pins are shaped and arranged to create turbulence
in a fluid that passes through the passage. 10. The air
distribution system of any of aspects 1-9, comprising a plurality
of plates and a plurality of protrusions, wherein each plate is
coupled one of the plurality of protrusions, wherein each of the
plurality of plates is spaced apart from each another, and wherein
the inlet of the passage is at least partially defined by a gap
between the respective outer edges of at least two of the plurality
of plates. 11. A turbine vane comprising:
[0050] a wall comprising an inner surface, an outer surface, and a
protrusion extending from the inner surface of the wall;
[0051] a plate spaced apart from the inner surface of the wall, the
plate comprising an outer edge wherein the plate is fixedly coupled
to the protrusion; and
[0052] an airfoil extending outwardly from the outer surface of the
wall; wherein a passage is defined between the plate and the inner
surface of the wall, and wherein an inlet of the passage is defined
by the outer edge of the plate.
12. The turbine vane of aspect 11, wherein a perimeter of the plate
defined by the outer edge of the plate is greater than a perimeter
of the protrusion which is fixedly coupled to the plate. 13. The
turbine vane of any of aspects 11 and 12, further comprising a
cavity within the airfoil, the passage having an outlet which is in
fluid communication with the cavity of the airfoil. 14. The turbine
vane of any of aspects 11 and 12, wherein the airfoil comprises a
boss which extends inwardly from the inner surface of the wall,
wherein the outlet of the passage is defined by an opening in the
boss. 15. The turbine vane of aspect 14, wherein the protrusion is
the boss of the airfoil. 16. The turbine vane of aspect 15, wherein
the plate encircles the boss of the airfoil. 17. The turbine vane
of any of aspects 11-16, wherein the wall comprises a raised
element extending transversely to and aligned with the outer edge
of the plate, wherein the inlet of the passage is at least
partially defined by a gap between the raised element of the wall
and the outer edge of the plate. 18. A method of cooling a
component of a turbine vane comprising:
[0053] supplying cooling air to a passage, wherein the passage is
defined between the wall of the turbine vane and a plate spaced
apart from the wall, wherein the plate is fixedly coupled to a
protrusion which extends between the plate and the wall, and
wherein an inlet of the passage is defined by an outer edge of the
plate; and
[0054] releasing the cooling air from the passage through an outlet
of the passage.
19. The method of aspect 18, wherein the cooling air is released
through an opening in the wall to an outer surface of the wall. 20.
The method of aspect 18, wherein the cooling air is released into a
cavity of an airfoil of the turbine vane.
* * * * *